EP1507959A1 - Ensemble pour la fixation axiale et radiale des aubes fixes d'un stator d'une turbine a gaz - Google Patents

Ensemble pour la fixation axiale et radiale des aubes fixes d'un stator d'une turbine a gaz

Info

Publication number
EP1507959A1
EP1507959A1 EP03737889A EP03737889A EP1507959A1 EP 1507959 A1 EP1507959 A1 EP 1507959A1 EP 03737889 A EP03737889 A EP 03737889A EP 03737889 A EP03737889 A EP 03737889A EP 1507959 A1 EP1507959 A1 EP 1507959A1
Authority
EP
European Patent Office
Prior art keywords
guide vanes
ring
guide
locking elements
gas turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP03737889A
Other languages
German (de)
English (en)
Other versions
EP1507959B1 (fr
Inventor
Werner Humhauser
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1507959A1 publication Critical patent/EP1507959A1/fr
Application granted granted Critical
Publication of EP1507959B1 publication Critical patent/EP1507959B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an arrangement according to the preamble of patent claim 1.
  • the stator of a gas turbine does not form an integral unit, but rather has critical connection and bearing points with regard to the column to be observed. Fixations taking into account the temperature gradients occurring between the turbine housing and the guide vane ring must be provided, the implementation of which can cause considerable difficulties. As a result of the limited space and poor accessibility, milling work on the abutment surfaces located on the turbine housing can only be carried out with great effort in order to implement the required fixings. This applies not only to the initial assembly, but also to rework as a result of wear during the operation of such gas turbines.
  • the invention has for its object to remedy this situation by a new design of the means for fixing the guide vanes of a vane ring of a gas turbine.
  • the guide vanes can be combined into a construction module by means of the new locking elements before they are inserted into the turbine, which leads to a simple partner interface and considerably simplifies assembly.
  • the new locking elements enable the guide vane rings to be fixed almost without play, directly on the spoke centering, if the previously required are eliminated Ring seals.
  • Fig. 1 is a sectional view of the guide and vane rings comprising low pressure part of a gas turbine and
  • Fig. 2 in an enlarged exploded view the locking elements associated with the guide vane tips of the guide vane ring according to the invention.
  • FIG. 1 shows a section of a gas turbine, designated overall by reference number 10, of its low-pressure part with a stator ST having guide vanes 12, 12 'and a rotor RT having rotor blades 14, 14', and the associated turbine housing 16.
  • the guide vanes and rotor blades are each combined into so-called guide vanes and rotor blade rings which, with their associated components, which are not described in more detail, form so-called partner components - namely the stator and the rotor mentioned - of the gas turbine 10 enclosed by the turbine housing 16.
  • the guide vane ring 13 formed by the guide vanes 12 projects between two rotor blade rings with their rotor blades 14 and 14 '.
  • a further guide vane ring 15 with guide vanes 12 ' is fixed upstream between the hub and the housing.
  • the guide vane ring 13, which is still to be described between the turbine housing 16 and a seal carrier 17 of the stator ST, is exposed to dilations caused by temperature gradients between the turbine housing and guide grille, which are accommodated via defined gaps.
  • the locking elements shown in FIG. 2 are used for fixing provided that are associated with each end of a guide vane 12 facing away from the hub.
  • these locking elements comprise a casing ring 18 with an axial stop surface 19 and with radial projections 21 including pairs of flat mating surfaces 20 for the purpose of accommodating corresponding flat bearing surfaces 24 on a downstream casing ring 18 ′′.
  • An axial one that can be clearly seen in FIG Extension of the casing ring 18 "also has mutually opposite rectangular recesses 27 and 27 ', which each serve to receive the legs 28, 28' of a U-shaped holding piece 30.
  • Each holding piece 30 has on its rear base an abutment surface 32, behind which a clamping bracket 35, which will be described, engages after the mounting of the guide vanes on the turbine housing.
  • the guide vanes 12 are aligned with corresponding mating surfaces with the mating surfaces 20 of the protrusions 21 of the casing ring 18, which, with its contact surface 19, is in axial contact with the guide vanes 12.
  • the in the recesses 27 and 27 'by means of the legs 28, 28' engaging holding pieces 30 fix the guide vanes 12 and the casing ring 18 on the casing ring 18 ′′, the latter being fixed and fixed on the turbine housing.
  • a positive locking located directly at the location of the usual spoke centering is formed, which is denoted overall by VE or VE 'in FIG. 1 and which is secured for each guide vane in each case by the spring clip 35 already mentioned.
  • the spring clips 35 engage with their free ends under the radially inner bearing surfaces 24 on the casing ring 18 ′′, more precisely on its axial extension.
  • the guide vane tips also have projections 41, 41 ', to which corresponding stop surfaces 42, 42' on the casing rings 18, 18 'are assigned.
  • the ends of the guide vanes 12 facing the seal carrier 17 of the stator ST carry sealing linings 44 known per se, the associated sealing fins 45 of which are arranged on the rotor part 46. LIST OF REFERENCE NUMBERS

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbine à gaz (10) comprenant au moins un stator, dont les aubes fixes (12) sont fixées axialement et radialement par l'intermédiaire d'éléments de blocage amovibles (18, 18', 18'', 30). Ces éléments de blocage comprennent une couronne périphérique (18), conçue sous forme de composant librement usinable et présentant des saillies (21) pourvues d'une surface de butée (19) et de surfaces de contact (20), ainsi qu'une pièce de retenue (30) pour chaque aube fixe (12), laquelle pièce de retenue s'engage sur une couronne périphérique en aval (18'') dans des évidements correspondants (27, 27'), ces pièces de retenue (30) étant maintenues par le biais d'étriers de ressort (35) dans leur position définie par les éléments de blocage.
EP03737889A 2002-05-28 2003-05-15 Ensemble pour la fixation axiale et radiale des aubes fixes d'un stator d'une turbine a gaz Expired - Lifetime EP1507959B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10223655 2002-05-28
DE10223655A DE10223655B3 (de) 2002-05-28 2002-05-28 Anordnung zum axialen und radialen Fixieren der Leitschaufeln eines Leitschaufelkranzes einer Gasturbine
PCT/DE2003/001568 WO2003102379A1 (fr) 2002-05-28 2003-05-15 Ensemble pour la fixation axiale et radiale des aubes fixes d'un stator d'une turbine a gaz

Publications (2)

Publication Number Publication Date
EP1507959A1 true EP1507959A1 (fr) 2005-02-23
EP1507959B1 EP1507959B1 (fr) 2006-11-29

Family

ID=29594175

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03737889A Expired - Lifetime EP1507959B1 (fr) 2002-05-28 2003-05-15 Ensemble pour la fixation axiale et radiale des aubes fixes d'un stator d'une turbine a gaz

Country Status (4)

Country Link
US (1) US7396206B2 (fr)
EP (1) EP1507959B1 (fr)
DE (2) DE10223655B3 (fr)
WO (1) WO2003102379A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2875534B1 (fr) 2004-09-21 2006-12-22 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz avec rotor comportant un corps monobloc
FR2875535B1 (fr) * 2004-09-21 2009-10-30 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
US8043044B2 (en) * 2008-09-11 2011-10-25 General Electric Company Load pin for compressor square base stator and method of use
US8534990B2 (en) * 2009-11-11 2013-09-17 Hamilton Sundstrand Corporation Inlet guide vane drive system with spring preload on mechanical linkage
US20130052024A1 (en) * 2011-08-24 2013-02-28 General Electric Company Turbine Nozzle Vane Retention System
US9932901B2 (en) 2015-05-11 2018-04-03 General Electric Company Shroud retention system with retention springs
US9828879B2 (en) 2015-05-11 2017-11-28 General Electric Company Shroud retention system with keyed retention clips

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2609176A (en) * 1950-01-21 1952-09-02 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2654566A (en) 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction
GB904138A (en) * 1959-01-23 1962-08-22 Bristol Siddeley Engines Ltd Improvements in or relating to stator structures, for example for axial flow gas turbine engines
GB1086432A (en) 1965-09-21 1967-10-11 Bristol Siddeley Engines Ltd Gas turbine engines
US3992126A (en) * 1975-03-25 1976-11-16 United Technologies Corporation Turbine cooling
GB1605310A (en) * 1975-05-30 1989-02-01 Rolls Royce Nozzle guide vane structure
FR2345605A1 (fr) 1976-03-25 1977-10-21 Snecma Dispositif de retenue pour aubes de soufflantes
FR2438165A1 (fr) * 1978-10-06 1980-04-30 Snecma Dispositif de regulation de temperature pour turbines a gaz
US4566851A (en) 1984-05-11 1986-01-28 United Technologies Corporation First stage turbine vane support structure
CA2070511C (fr) 1991-07-22 2001-08-21 Steven Milo Toborg Support de distributeur de turbine
US5201846A (en) 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
FR2697285B1 (fr) * 1992-10-28 1994-11-25 Snecma Système de verrouillage d'extrémités d'aubes.
US5441385A (en) * 1993-12-13 1995-08-15 Solar Turbines Incorporated Turbine nozzle/nozzle support structure
US6095750A (en) 1998-12-21 2000-08-01 General Electric Company Turbine nozzle assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO03102379A1 *

Also Published As

Publication number Publication date
US20050238490A1 (en) 2005-10-27
DE50305849D1 (de) 2007-01-11
WO2003102379A1 (fr) 2003-12-11
DE10223655B3 (de) 2004-02-12
EP1507959B1 (fr) 2006-11-29
US7396206B2 (en) 2008-07-08

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